CN102806665A - Method for producing T-shaped stringer with angle of other than 90 degrees between web and foot - Google Patents
Method for producing T-shaped stringer with angle of other than 90 degrees between web and foot Download PDFInfo
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- CN102806665A CN102806665A CN2012102357279A CN201210235727A CN102806665A CN 102806665 A CN102806665 A CN 102806665A CN 2012102357279 A CN2012102357279 A CN 2012102357279A CN 201210235727 A CN201210235727 A CN 201210235727A CN 102806665 A CN102806665 A CN 102806665A
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- stringer
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- web
- base portion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49885—Assembling or joining with coating before or during assembling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The invention relates to a method for producing a T-shaped stringer with an angle of other than 90 degrees between a web and a foot, and specifically relates to a method for producing a T-shaped stringer (1) with an angle of other than 90 degrees between a web (2) and a foot (3), wherein the T-shaped stringer (1) includes the stringer web and the stringer foot. The method comprises: two hot-formed L-shaped half-stringers are positioned together to form a T-shaped stringer, and the T-shaped stringer is positioned in an invar alloy angle, leaving spaces between the stringer web and the invar alloy angle. Thereafter, a heating device (7) moves on the surface of the stringer foot (3) and a roller (8) slides on the surface of the stringer foot (3) so as to adapt the geometrical shape of the stringer foot to the geometrical shape of the invar alloy angle. The obtained T-shaped stringer is combined on a cured surface with a line of adhesive placed between the stringer and the cured surface, and the T-shaped stringer is cured.
Description
Technical field
The invention belongs to aircraft industry, and relate to the airborne vehicle stringer.Especially, it relates to T-shape composite stringers and the method for making it.
Background technology
In airframe, stringer or spar or reinforcement are the strips of being processed by carbon fiber.Several bands are combined in the part (like wing, tailplane etc.) to set up airborne vehicle on the solidified surface jointly.
The utmost point common type of stringer is to have " T " shape cross section that limits stringer web and stringer base portion.
The manufacturing approach that is generally used for " T " shape stringer of airborne vehicle comprises: the first step; The thermoforming laminate; Have the half stringer geometry of " L " tee section with completion, and second step, half stringer of two thermoformings is put together to accomplish " T " shape stringer.Then, " T " shape stringer combines on solidified surface jointly, between them, has cementing line.
This method comprised for the 3rd step, was cure cycle.Usually, tools of solidifying is about 90 ° invar alloy angle, and it is placed to the profile of thermoforming " T " the shape stringer of deferring in the vacuum bag of cure cycle.Should be noted in the discussion above that the invar angle just in time is 90 ° when stringer is flat surfaces by the common surface that combines.
When the surface was bent, the base portion of stringer and the angle between the web slightly changed, and therefore made to necessitate from 90 ° of angles that change the invar angle.Under those situation, the T-shape stringer not exclusively adapts to invar alloy angle geometry and is equipped with deviation with respect to stringer theoretical bits from the teeth outwards is possible.
Under prior art, when the invar alloy angle of the geometry that has the angle that is different from 90 ° must be used, employed solution was that half stringer with two " L " shapes puts together, thereby forms the T-shape stringer with different height.The problem of this solution is that the stringer base portion does not have identical geometry with its surface that need be placed.When stringer is placed on its position, between stringer base portion and surface, free space is arranged.Therefore, in conjunction with being a low-quality combination, possibly in structure, cause later problem.
In case being the stringer base portion, the another kind of solution of from prior art, knowing is cured, just with the base curve of stringer its geometry is adapted to the geometry on its surface that is placed.Problem is that this bending of stringer base portion can produce visible fold, and the difficult additional element of in stringer, assembling.
Prior art has shown the distinct methods of " T " shape stringer manufacture process.Document EP 2 052 846A1 have disclosed the method that a kind of formation has " T " shape composite construction of radius filler.Document US 2009/0107312
A1 discloses a kind of crooked method and apparatus of in composite plate, creating.Document US 5 827 383A show a kind of method of making the reinforcement assembly.
Summary of the invention
The purpose of this invention is to provide a kind of method of making " T " shape stringer that must be placed on the inclined surface.In these cases, be manufactured on that to have the stringer that is different from 90 ° of angles between stringer web and the stringer base portion be necessary.
Therefore, another object of the present invention provides on inclined surface the stringer in its theoretical position assembling, thereby it is placed and avoids the use of adapter and help its position of stringer maintenance at this place.
The present invention is designed to overcome the above-mentioned defective of " T " shape stringer that must be placed on the inclined surface.
Through the present invention, term " invar " (invar) usually also is called as FeNi36 (at U.S. 64FeNi), is the alloy of nickel (36%) and steel (64%), and is famous with its unique low thermal coefficient of expansion (CTE).Title " invar " comes from word " constant (invariable) ", refers to it and lacks expansion or contraction with variations in temperature.
Therefore; Invar alloy has shown extremely low expansion in the temperature of environment around; Make them in application, be particularly useful; In said application,, need minimum thermal expansion and higher-dimension stability in the precision instrument of scientific instrument of electronic product and other types and so on as at photoelectric device, optics and laser work platform.They also have very big applicability in the manufacturing of the instrument that is used for cured composite material.Term " composite " comprises the material of various heterogeneous body polymer bases and non-polymer base, is commonly called " enhancing compound ", " carbon fiber composite " or known in the prior art other terms.
The present invention provides a kind of manufacturing approach that must be placed on " T " shape stringer on the curved surface.In this case, the base portion of stringer and the angle between the web are slightly from 90 ° of changes.The invar alloy angle of the curing of the stringer that is used for being mentioned has and has the geometry that is different from 90 ° angle between part that covers the stringer base portion and the part that covers the stringer web.
Therefore, the invention describes the manufacturing approach of " T " shape stringer that is used for airborne vehicle, and this method comprises with stringer web and stringer base portion:
---the first step, thermoforming carbon fiber layer casting die is to realize half stringer of band " L " shape cross section; For this step, the angle between stringer base portion and the stringer web is 90 °;
---in second step, " L " shape half stringer of two thermoformings is put together to form " T " shape stringer; Wherein this two and half stringer puts together with differing heights;
---in the 3rd step, in the invar alloy angle, settle " T " shape stringer, and between stringer web and invar alloy angle, leave the gap;
---the 4th step, mobile heating device on the stringer base surface, and the roller that on said stringer base surface, slides;
---the 5th step, common bonding resulting " T " shape stringer on solidified surface, and between stringer and solidified surface, have tack line; And
---in the 6th step, solidify the T-shape stringer that is obtained.
Gap between stringer web and invar alloy angle before heating and mobile roller, for the stringer web thickness between 6 to 10mm, should be between 4 to 6mm, and for the stringer web thickness of 10-15mm, should be between 7 to 9mm.Under any circumstance, it is important to guarantee that stringer does not contact (before curing, uncured glass fibre and uncured carbon fiber reinforced polymer-CFRP-material have extraordinary location (tacking) performance) at any point with the invar angle.If between uncured T shape stringer and invar alloy angle, have release film, then this gap can be reduced to 2mm for thickness reaches 15mm.
When the 3rd of this method of enforcement went on foot, be inverted to allow in the invar alloy angle, placing stringer, to make and can on the surface of stringer base portion, work at the invar alloy angle.
When the 4th of this method of enforcement went on foot, for example heater can be dryer or infrared lamp.Mentioned heater is used to heat the surface of stringer base portion, so its shape can be modified, and still temperature is always low than solidifying the needed temperature of " T " shape stringer.It possibly heat and reaches 110 ℃, but with surface that the invar angle directly contacts in the radius region measured, recommend for 40 °, in the radius region of on the surface that will be placed on the solidified surface, measuring, recommend for 60 °.
When the 4th of this method of enforcement went on foot, behind mobile heating device on the surface of stringer base portion, when it was hot, roller slided on said surface to obtain the form desired geometries of stringer.
The bar that slides on the surface of stringer base portion, enable manual or slip automatically.
Because the stringer base portion has the different height value, so bar has the covering of flexible material, and bar must be prepared into to absorb the variation of these height.Equally, also there is different thickness on the surface that stringer is placed, and this varied in thickness must be handled in the bar surface.
This manufacture process produces these stringers that can ideally fit in the surface that stringer is placed; Thereby optimize the connection between surface and stringer, and eliminate use miscellaneous part for example chock to fill up the gap that produces through additive method well known in the prior art.In case stringer is assembled, they can not move with respect to their theoretical position, thereby improve the reliability of made forging piece.
In addition, because the following fact: stringer is fit to the invar alloy angle fully along radius region, so produce any distortion as the material Shi Buhui that is cured.
This manufacture process can not produce fold along the stringer radius.Fold along the stringer radius has reduced its mechanical property; Therefore, this method can produce the stringer stronger than additive method well known in the prior art.
Description of drawings
The present invention will based on following to embodiments of the invention and accompanying drawing detailed description and understood fully, therefore embodiment and accompanying drawing only do not limit the present invention as an example and quilt is showed, wherein:
Fig. 1 a has shown the theoretical geometry that will be placed on the curing stringer on the flat surfaces.
Fig. 1 b has shown the theoretical geometry that will be placed on the curing stringer on the curved surface.
Fig. 2 has shown " T " shape stringer that will be cured on the solidified surface.
Fig. 3 has shown and has made the solution that will be placed on stringer on the curved surface in the prior art.This two and half stringer puts together with different height.
Fig. 4 has shown the invar angle that is different from 90 ° of angles that has that is designed to make the stringer that will be placed on the curved surface.
Fig. 5 has shown the stringer that has in the invar angle that is different from 90 ° of angles, heater and roller, and it uses to revise the geometry of stringer base portion in the method.
Reference numeral
1: the T-shape stringer
2: the stringer web
3: the stringer base portion
4: solidified surface
5: tack line
6: the invar alloy angle
7: heater
8: roller
A: the angle between stringer web and the stringer base portion
B: the distance between the half stringer base portion
C: gap
The specific embodiment
Following description only provides for helping reader, and is not intended to limit by any way the present invention who illustrates like claim.
Fig. 1 a has shown the theoretical geometry that must be placed on the curing stringer on the flat surfaces.Angle A between stringer web 2 and stringer base portion 3 is 90 °.
Fig. 1 b has shown the theoretical geometry that must be placed on the stringer on the curved surface.Angle A between stringer web 2 and stringer base portion 3 is different from 90 °.
Show " T " shape stringer 1 among Fig. 2, be attached to solidified surface 4 jointly, between stringer 1 and solidified surface 4, had tack line 5.In addition, invar alloy angle 6 is placed to the profile of following thermoforming " T " shape stringer 1.
When the surface is bent, change a little at the base portion 3 of stringer and the angle A between the web 2, be different from 90 ° angle thereby make the invar alloy angle between the part of part that covers the stringer web and covering stringer base portion, have.Shown among Fig. 3 that from a solution well known in the prior art two " L " shape half stringers that wherein form the T-shape stringer are put together with different height, between stringer base portion 3, leave apart from B.Angle A between stringer web 2 and the stringer base portion 3 is 90 ° in this case.
Solution shown in Figure 3 has been explained the major defect of prior art: if do not make other steps, and the geometry at the not adaptive invar of " T " shape stringer angle then.When making stringer when in panel, fitting on its theoretical position, this situation possibly cause deviation.This is faulty adaptive as shown in Figure 4.
The present invention proposes a kind of manufacturing approach that must be placed on " T " shape stringer on the curved surface.Through this method, obtained ideally to be adapted to the lip-deep stringer that it need be placed.
Employed in the method invar alloy angle is designed to obtain to have the stringer that between stringer web 2 and stringer base portion 3, is different from 90 ° angle A.
In the method, before being cured, the geometry of stringer is suitable for the geometry at invar alloy angle 6, makes its theoretical shape that adopts it to have when it is cured.
Therefore, the invention describes a kind of manufacturing approach that is used for " T " shape stringer that has stringer web and stringer base portion of airborne vehicle, as shown in Figure 5, this method comprises:
---the first step, thermoforming carbon fiber layer casting die is to realize half stringer of band " L " shape cross section;
---in second step, " L " shape half stringer of two thermoformings is put together to form " T " shape stringer 1;
---in the 3rd step, in the invar alloy angle, settle " T " shape stringer, and between stringer web 2 and invar alloy angle 6, leave clearance C;
---the 4th the step, mobile heating device 7 on stringer base portion 3 surfaces, and on said stringer base portion 3 surfaces slip roller 8;
---the 5th step, common bonding resulting " T " shape stringer 1 on solidified surface 4, and between stringer 1 and solidified surface 4, have tack line 5; And
---in the 6th step, solidify the T-shape stringer 1 that is obtained.
In a preferred embodiment of the invention, the clearance C that between stringer web 2 and invar alloy angle 6, leaves is 5mm.
Gap between stringer web and invar alloy angle before heating and mobile roller, for the stringer web thickness between 6 to 10mm, should be between 4 to 6mm, and for the stringer web thickness of 10-15mm, should be between 7 to 9mm.Under any circumstance, it is important to guarantee that stringer does not contact (before curing, uncured glass fibre and uncured CFRP material have extraordinary location (tacking) performance) at any point with the invar angle.If between uncured T shape stringer and invar alloy angle, have release film, then this gap can be reduced to 2mm for thickness reaches 15mm.
In another embodiment of the present invention, when the 4th when step of carrying out method, heater 7 is infrared lamps, even also can be with any other means easily.Experience shows, uses other heaters 7 that are different from infrared lamp can produce bigger heat loss, and therefore, the movement velocity of heater 7 must be lowered, thereby improves production time and production cost.Therefore, when making according to this method, infrared lamp is the heater 7 that is fit to.
The advisory speed that mobile heating device 7 is gone up on stringer base portion 3 surfaces in embodiments of the present invention is 1m/5min.In a preferred embodiment of the invention, heater 7 is to move automatically.
In a preferred embodiment, stringer base portion 3 lip-deep temperature are lower than 60 °, and under any circumstance are lower than and need solidify the required temperature of stringer 1.
In the 4th step of this method, be used to that the stringer base portion provides necessary bending so that they are installed in the lip-deep roller 8 that stringer will be placed, after heater 7 is moved on said surface, on stringer base portion 3 surfaces, slide.
In a preferred embodiment of the invention, roller 8 has the covering that flexible material is processed.
Claims (8)
1. be used between web and base portion, having the manufacturing approach of " T " shape stringer that is different from 90 ° of angles, wherein " T " shape stringer (1) has stringer web (2) and stringer base portion (3), and said method comprises:
---the first step, thermoforming carbon fiber layer casting die is to obtain to have half stringer of " L " shape cross section;
---in second step, " L " shape half stringer of two thermoformings is put together to form " T " shape stringer;
---the 3rd step, said " T " shape stringer (1) is placed in the invar alloy angle, between said stringer web (2) and said invar alloy angle (6), leave gap (C);
---the 4th the step, mobile heating device on the stringer base surface (7), and on said stringer base portion (3) surface slip roller (8);
---the 5th step, common combination resulting " T " shape stringer (1) on solidified surface, and between said stringer (1) and said solidified surface (4), have tack line (5); And
---in the 6th step, solidify the T-shape stringer (1) that is obtained.
2. method according to claim 1; Wherein, when implementing the 3rd step of said method, for the stringer web thickness between 6 to 10mm; Said gap (C) is included between 4 to 6mm, thereby guarantees that under any circumstance said stringer (1) is not attached to said invar angle (6).
3. method according to claim 1; Wherein, when implementing the 3rd step of said method, for the stringer web thickness between 10 to 15mm; Said gap (C) is included between 7 to 9mm, thereby guarantees that under any circumstance said stringer (1) is not attached to said invar angle (6).
4. method according to claim 1; Wherein, When implementing the 3rd step of said method, if between uncured T shape stringer (1) and said invar alloy angle (6), have release film, then said gap (C) can be reduced to 2mm for the stringer web thickness that reaches 15mm.
5. according to the described method of aforementioned arbitrary claim, wherein heater (7) is an infrared lamp.
6. according to the described method of aforementioned arbitrary claim, wherein said roller (8) has the covering of being processed by flexible material.
7. according to the described method of aforementioned arbitrary claim, wherein heater (7) mobile speed on said stringer base portion (3) surface is 1m/5min.
8. according to the T-shape stringer that between web and base portion, has the angle that is different from 90 ° of aforementioned arbitrary claim manufacturing.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES201130889A ES2400129B1 (en) | 2011-05-30 | 2011-05-30 | METHOD OF MANUFACTURING OF LARGUERILLOS WITH FORM OF "T" WITH A DIFFERENT ANGLE OF 90� BETWEEN THE SOUL AND THE FOOT |
| ESP201130889 | 2011-05-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102806665A true CN102806665A (en) | 2012-12-05 |
| CN102806665B CN102806665B (en) | 2016-09-28 |
Family
ID=47230611
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210235727.9A Active CN102806665B (en) | 2011-05-30 | 2012-05-30 | For having the manufacture method of the "T"-shaped stringer being different from 90 ° of angles between web and base portion |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US8943664B2 (en) |
| CN (1) | CN102806665B (en) |
| ES (1) | ES2400129B1 (en) |
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| JP2015072041A (en) * | 2013-10-02 | 2015-04-16 | 三菱重工業株式会社 | Joint and aircraft structure |
| CN106670648A (en) * | 2015-11-06 | 2017-05-17 | 波音公司 | Edge preparation for laser welding |
| CN107150785A (en) * | 2016-03-04 | 2017-09-12 | 波音公司 | Conductive fillet filling system and method |
| CN108262992A (en) * | 2016-12-30 | 2018-07-10 | 空中客车德国运营有限责任公司 | For by reinforcing fiber formable layer for preforming T shapes section bar diaphragm tool |
| CN108262991A (en) * | 2016-12-30 | 2018-07-10 | 空中客车德国运营有限责任公司 | For the tool of forming T-shaped semi-finished product |
| CN110267800A (en) * | 2017-01-12 | 2019-09-20 | 维斯塔斯风力系统有限公司 | Method and apparatus for assembling the wind turbine blade with internal web |
| CN112406755A (en) * | 2020-11-27 | 2021-02-26 | 中国第一汽车股份有限公司 | Bumper beam and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2397727B1 (en) * | 2010-10-28 | 2014-01-17 | Airbus Operations, S.L. | REUSABLE RETAINERS FOR COENCOLADO OF UNCURED LARGUERILLOS. |
| US9399509B2 (en) * | 2014-04-10 | 2016-07-26 | The Boeing Company | Vent stringer fitting |
| US9399510B2 (en) * | 2014-08-20 | 2016-07-26 | The Boeing Company | Hat stringer closeout fitting and method of making same |
| DE102018110123A1 (en) * | 2018-04-26 | 2019-10-31 | Airbus Operations Gmbh | Method for producing a three-dimensional preform made of reinforcing fibers |
| GB2575102A (en) * | 2018-06-29 | 2020-01-01 | Airbus Operations Ltd | Duct stringer with bulkhead |
| EP4353454A1 (en) * | 2022-10-11 | 2024-04-17 | Airbus Operations, S.L.U. | Method for manufacting stringers for aircrafts and stringer obtained by said method |
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| JP2015072041A (en) * | 2013-10-02 | 2015-04-16 | 三菱重工業株式会社 | Joint and aircraft structure |
| CN105518315A (en) * | 2013-10-02 | 2016-04-20 | 三菱重工业株式会社 | Joint, and aircraft structure |
| US10040538B2 (en) | 2013-10-02 | 2018-08-07 | Mitsubishi Heavy Industries, Ltd. | Joint, and aircraft structure |
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| CN108262991A (en) * | 2016-12-30 | 2018-07-10 | 空中客车德国运营有限责任公司 | For the tool of forming T-shaped semi-finished product |
| CN108262992B (en) * | 2016-12-30 | 2021-08-17 | 空中客车德国运营有限责任公司 | Membrane tool for shaping a reinforcing fiber layer into a preformed T-shaped profile |
| CN110267800A (en) * | 2017-01-12 | 2019-09-20 | 维斯塔斯风力系统有限公司 | Method and apparatus for assembling the wind turbine blade with internal web |
| CN110267800B (en) * | 2017-01-12 | 2021-01-12 | 维斯塔斯风力系统有限公司 | Method and apparatus for assembling a wind turbine blade with an internal web |
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| CN112406755A (en) * | 2020-11-27 | 2021-02-26 | 中国第一汽车股份有限公司 | Bumper beam and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| US20130133171A1 (en) | 2013-05-30 |
| CN102806665B (en) | 2016-09-28 |
| ES2400129R1 (en) | 2013-08-12 |
| US8943664B2 (en) | 2015-02-03 |
| ES2400129B1 (en) | 2014-06-18 |
| ES2400129A2 (en) | 2013-04-05 |
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